气膜孔排布对排气系统中心锥冷却和红外辐射特性的影响

王旭; 张靖周; 单勇

doi:10.13224/j.cnki.jasp.2016.04.009

气膜孔排布对排气系统中心锥冷却和红外辐射特性的影响

doi: 10.13224/j.cnki.jasp.2016.04.009

南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室, 南京 210016

基金项目:

国家自然科学基金(51306088)

江苏省自然科学基金(BK20130790)

详细信息

作者简介:
王旭(1990-),男,河北秦皇岛人,硕士生,主要从事红外抑制、传热与燃烧研究.

中图分类号: V231.3
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- 被引次数: 0
出版历程
- 收稿日期: 2014-08-10
- 刊出日期: 2016-04-28

Effects of film hole arrangement on central-cone cooling and infrared radiation characteristics of exhaust system

Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing Univerisity of Aeronautics and Astronautics, Nanjing 210016, China

摘要

摘要: 运用计算流体力学/红外辐射(CFD/IR)的数值模拟方法,以涡扇发动机排气系统为原型,对中心锥表面气膜冷却方案进行了数值研究,并揭示了中心锥冷却对红外辐射特征的作用效果.研究表明:气膜冷却中心锥可有效降低中心锥表面的温度,抑制排气系统在0°~15°范围内的红外辐射.在所研究的诸多方案中,与无冷却的涡扇排气系统相比,中心锥表面温度可以降低282K,0°方向上可降低总体红外辐射约57%.
- 涡扇发动机 /
- 排气系统 /
- 中心锥冷却 /
- 气膜冷却 /
- 红外辐射
Abstract: The axisymmetric convergent-expansion nozzle exhaust system of a certain turbofan engine was taken as a prototype wherein the film cooling schemes on the central-cone surface were numerically investigated by CFD/IR methods. The cooling schemes were compared and the cooling action of central-cone surface on the infrared radiation characteristics was revealed. The results show that the film cooling on the central-cone surface could effectively decrease the surface temperature, and suppress the infrared radiation intensity between 0 degree and 15 degree viewed from backward direction. The best cooling scheme achieved about 282K decrease on the central-cone surface as well as 57% relative decrease of infrared radiation intensity on 0 degree direction by comparing with the prototype exhaust system.
- turbofan engine /
- exhaust system /
- central-cone cooling /
- film cooling /
- infrared radiation

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参考文献(18)

[1]	Mahulikar S P,Sonawane H R,Rao G A.Infrared signature studies of aerospace vehicles[J].Progress in Aerospace Sciences,2007,43(7):218-245.
[2]	桑建华,张宗斌.红外隐身技术发展综述[J].红外与激光工程,2013,42(1):14-19. SANG Jianhua,ZHANG Zongbin.Development trends of infrared stealth technology[J].Infrared and Laser Engineering,2013,42(1):14-19.(in Chinese)
[3]	Capone F J.The nonaxisymmetric nozzle:it is for real[R].AIAA 79-1810,1979.
[4]	郑礼宝.全尺寸二元喷管红外辐射特性研究[J].航空学报,2002,23(2):140-142. ZHENG Libao.Infrared emissions from turbojet with two-dimensional nozzle[J].Acta Aeronautica et Astronautica Sinica,2002,23(2):140-142.(in Chinese)
[5]	范仁钰,张靖周,单勇.遮挡板结构对二元喷管红外辐射特性的影响[J].航空动力学报,2011,26(2):343-348. FANG Renyu,ZHANG Jingzhou,SHAN Yong.Effects of sheltering baffles on the infrared radiation characteristics of two-dimensional nozzles[J].Journal of Aerospace Power,2011,26(2):343-348.(in Chinese)
[6]	罗明东,吉洪湖,黄伟,等.涡扇发动机二元喷管的红外光谱辐射特性实验[J].推进技术,2007,28(4):394-398. LUO Mingdong,JI Honghu,HUANG Wei,et al.Experiment on spectral infrared radiant characteristics of two-dimensional nozzles of turbofan engine[J].Journal of Propulsion Technology,2007,28(4):394-398.(in Chinese)
[7]	王宏亮,张靖周,单勇.球型收敛调节片喷管红外特性数值研究[J].航空学报,2009,30(9):1576-1582. WANG Hongliang,ZHANG Jingzhou,SHAN Yong.Numerical study on infrared radiation characteristics of spherical convergent flap nozzles[J].Acta Aeronautica et Astronautica Sinica,2009,30(9):1576-1582.(in Chinese)
[8]	杨承宇,张靖周,单勇.单边膨胀喷管红外辐射特性的数值模拟[J].航空学报,2010,31(10):1919-1926. YANG Chengyu,ZHANG Jingzhou,SHAN Yong.Numerical simulation on infrared radiation characteristics of single expansion ramp nozzles[J].Acta Aeronautica et Astronautica Sinica,2010,31(10):1919-1926.(in Chinese)
[9]	刘长春,吉洪湖,李娜,等.一种二元S弯喷管的红外辐射特性数值研究[J].工程热物理学报,2010,31(9):1567-1570. LIU Changchun,JI Honghu,LI Na,et al.Numerical simulation on infrared radiant characteristics of 2D S-nozzles[J].Journal of Engineering Thermophysics,2010,31(9):1567-1570.(in Chinese)
[10]	张少丽,单勇,张靖周,等.单边膨胀矢量喷管气动和红外特性研究[J].航空学报,2012,33(8):1406-1416. ZHANG Shaoli,SHAN Yong,ZHANG Jingzhou,et al.Research on the aerodynamic and infrared radiation characteristics of single expansion ramp vector nozzle[J].Acta Aeronautica et Astronautica Sinica,2012,33(8):1406-1416.(in Chinese)
[11]	Nosek S M,Straight D M.Heat-transfer characteristics of partially film cooled plug nozzle on a J-85 afterburning turbojet engine[R].NASA TM X-3362,1976.
[12]	李卒,江勇,林杰.不同冷却方式对中心锥冷却效果的影响[J].空军工程大学学报:自然科学版,2013,14(5):5-8. LI Zu,JIANG Yong,LIN Jie.Influence of different cooling methods on core cooling effectiveness[J].Journal of Air Force Engineering University:Natural Science Edition,2013,14(5):5-8.(in Chinese)
[13]	陈俊,吉洪湖.二元塞式喷管红外特性及壁面降温的红外抑制效果计算[J].航空动力学报,2012,27(11):2429-2435. CHEN Jun,JI Honghu.Numerical simulation of the infrared radiation characteristics and infrared restraining effect of lower wall temperature for two-dimensional plug nozzle[J].Journal of Aerospace Power,2012,27(11):2429-2435.(in Chinese)
[14]	王殿磊,张勃,吉洪湖,等.气膜孔布置形式对发动机中心锥冷却与红外抑制特性的影响[J].红外技术,2012,34(3):159-163. WANG Dianlei,ZHANG Bo,JI Honghu,et al.Investigation of effect of hole arrangement on cone cooling and infrared radiation characteristics[J].Infrared Technology,2012,34(3):159-163.(in Chinese)
[15]	单勇,张靖周,邵万仁,等.涡扇发动机排气系统中心锥气膜冷却结构的气动和红外辐射特性实验[J].航空动力学报,2012,27(1):9-15. SHAN Yong,ZHANG Jingzhou,SHAO Wanren,et al.Experiments on aerodynamic and infrared radiation characteristics of film-cooling center-body exhaust system for a turbofan engine[J].Journal of Aerospace Power,2012,27(1):9-15.(in Chinese)
[16]	张勃,吉洪湖,张宗斌,等.中心锥冷却对喷管腔体红外辐射的抑制作用数值分析[J].航空动力学报,2012,27(3):560-565. ZHANG Bo,JI Honghu,ZHANG Zongbin,et al.Numerical investigation of thermal radiation characteristics of nozzle cavities with center con cooled[J].Journal of Aerospace Power,2012,27(3):560-565.(in Chinese)
[17]	Shan Y,Zhang J Z.Numerical investigation of flow mixture enhancement and infrared radiation shield by lobed forced mixer[J].Applied Thermal Engineering,2009,29(17/18):3687-3695.
[18]	Pan C X,Zhang J Z,Shan Y.Modeling and analysis of helicopter thermal and infrared radiation[J].Chinese Journal of Aeronautics,2011,24(5):558-567.